EP0267474A1 - Rocket launch tubes - Google Patents

Rocket launch tubes Download PDF

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Publication number
EP0267474A1
EP0267474A1 EP87115531A EP87115531A EP0267474A1 EP 0267474 A1 EP0267474 A1 EP 0267474A1 EP 87115531 A EP87115531 A EP 87115531A EP 87115531 A EP87115531 A EP 87115531A EP 0267474 A1 EP0267474 A1 EP 0267474A1
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EP
European Patent Office
Prior art keywords
housing
guide device
rocket
container
rotations
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP87115531A
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German (de)
French (fr)
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EP0267474B1 (en
Inventor
Rainer Schöffl
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Dynamit Nobel AG
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Dynamit Nobel AG
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Publication date
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Publication of EP0267474A1 publication Critical patent/EP0267474A1/en
Application granted granted Critical
Publication of EP0267474B1 publication Critical patent/EP0267474B1/en
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F41—WEAPONS
    • F41F—APPARATUS FOR LAUNCHING PROJECTILES OR MISSILES FROM BARRELS, e.g. CANNONS; LAUNCHERS FOR ROCKETS OR TORPEDOES; HARPOON GUNS
    • F41F3/00—Rocket or torpedo launchers
    • F41F3/04—Rocket or torpedo launchers for rockets
    • F41F3/06—Rocket or torpedo launchers for rockets from aircraft
    • F41F3/065—Rocket pods, i.e. detachable containers for launching a plurality of rockets

Definitions

  • the invention relates to a launching container for rockets according to the preamble of patent claim 1.
  • Launch containers for rockets which have a guiding device in the form of a plurality of launch tubes, each of which receives a rocket.
  • the guide device is firmly connected to the container housing.
  • the container structure is either movable, for example in the case of rocket launchers mounted on vehicles, or rigidly, for example in the case of launch containers attached to aircraft, connected to the respective carrier (vehicle or aircraft). If the carrier has an inclined position when the rocket is launched, a directional error of the rocket trajectory occurs. The inclined position has a particularly serious effect if the missile is provided with aerodynamic surfaces which act only in one direction and which have the task of converting the missile's trajectory into a specific one Change direction. If the launch container was tilted, the direction of flight of the rocket would be falsified. It is therefore necessary to bring the carrier into a horizontal position at the time of the rocket launch. In the case of moving carriers, for example airplanes or vehicles, this is only incomplete or not possible at all.
  • the invention has for its object to form a launching container according to the preamble of claim 1 so that it enables a rocket launch in a defined position regardless of the respective position of the carrier.
  • the guide device is rotatable relative to the housing, and a stabilizing device ensures that the angle of rotation of the guide device with respect to the housing is adjusted so that any changes in the angle of rotation of the housing are compensated for.
  • the guide device therefore takes up an angle of rotation with respect to the housing, which at the respective time is opposite to the angle of rotation of the housing relative to an earth-based reference system.
  • the stabilization device can have an angle detector for determining rotations of the housing or the guide device with respect to the reference system, and a mechanical rotary drive for the guide device.
  • the reference system can be used for can be defined, for example, by a gyroscope which determines the deviation of the actual roll position of the guide device from the desired roll angle, the gyroscope being able to be arranged either in the carrier or in the starting container.
  • An electromechanical or an electrohydraulic system is preferably used as the drive system, but other systems can also be used, for example magnetic, pneumatic or pyrotechnic systems, the energy required either being supplied by the carrier or being generated in the starting container itself.
  • the latter can exist, for example, in starter containers on aircraft by means of a ram-air turbine and a connected power generator, so that a starter container that is completely autonomous in terms of roll stabilization can be created if the angle detector and the system specifying the reference position are also located in the starter container.
  • the starting container shown in Fig. 1 is attached to the outside of an aircraft. It has a housing 1 which is provided with suspension eyes 2 and in which the guide device 3 is arranged.
  • the housing 1 is open at the front ends, and it contains annular bearings 4, in which the guide device 3 is rotatable about the longitudinal axis of the housing.
  • the guide device 3 contains several starting tubes 5, which extend through the entire length of the housing 1 and are open at both ends.
  • the starting tubes 5 are arranged with their axes on a circle running coaxially to the longitudinal axis of the housing and distributed on this circle with uniform circumferential distances.
  • a servo motor 6 is fastened, the output shaft of which drives a sprocket segment 8 via a toothed wheel 7, which is fastened to the guide device 3 coaxially to its longitudinal axis.
  • the servo motor 6 can thus rotate the guide device 3 mounted in the bearings 4 around its longitudinal axis.
  • the control system 10, 11 for stabilizing the roll angle is located in a central tube 9 of the guide device which is closed at both ends.
  • An angle detector 10 gives the control electronics 11 a signal which corresponds to the deviation of the roll angle (the angle of rotation about the longitudinal axis of the guide device) with respect to a set roll angle defined on the basis of an earth-bound reference system. If the angle detector 10 detects a deviation of the actual position from the target position, the control electronics 11 send a corresponding control command to the servo motor 6, which then rotates the guide device 3 about its longitudinal axis so that it is independent of the position of the housing 1 or the carrier holding the housing always assumes the desired angle.
  • Fig. 2 shows schematically the main elements of the starting container of Fig. 1 with the corresponding control or signal lines.
  • the guide device 3, which is rotatably mounted in the housing 1, contains the control system 11, 12 with the angle detector 10 and the evaluation electronics 11.
  • the angle detector 10 is connected to the evaluation electronics 11 via signal and power lines 12.
  • a control line 13 leads from the evaluation electronics 11 to the servo motor 6.
  • the energy source 14 located in the aircraft is connected to the control system 10 and the servo motor 6 via supply lines 15, 16.
  • Fig. 3 to 5 show another embodiment of the starting container, in which an aerodynamically acting stabilizing device is provided.
  • the guide device 3 which contains a plurality of starting tubes 5 arranged in a ring shape, is rotatably mounted in pivot bearings 4.
  • two V-shaped guide elements 17 are attached, which on the from Housing 1 protruding rear end of the guide device 3 are arranged and protrude laterally beyond the housing 1.
  • the guide elements 17 are exposed to the outside air flow, which strives to maintain the positions of the guide elements 17 and thus to prevent or minimize rotation of the guide device 3 about its longitudinal axis.
  • the guide device 3 is freely rotatably mounted in the housing 1 without a drive device being provided. If the carrier aircraft takes an inclined position in flight, the aerodynamic forces acting on the guide elements 17 cause a moment that keeps the guide device 3 in the desired position.

Abstract

1. Rocket launch tube with a housing (1) in which a guide arrangement (3) for receipt of at least one rocket is arranged, wherein the housing (1) is connectible with a support, characterised in that the guide arrangement (3) is rotatable in the housing (1) and that a stabilizing arrangement (6, 7, 8, 10, 11; 17) is provided which counteracts the rotations of the housing (1) by counter-rotations of the guide arrangement (3) relative to the housing.

Description

Die Erfindung betrifft einen Startbehälter für Raketen nach dem Oberbegriff des Patentanspruchs 1.The invention relates to a launching container for rockets according to the preamble of patent claim 1.

Bekannt sind Startbehälter für Raketen, die eine Führungseinrichtung in Form mehrerer Startrohre, von denen jedes eine Rakete aufnimmt, aufweisen. Die Führungseinrichtung ist mit dem Behältergehäuse fest verbunden. Die Behälterstruktur ist entweder beweglich, z.B. bei auf Fahrzeugen richtbar angebrachten Raketenwerfern, oder starr, z.B. bei an Flugzeugen befestigten Startbehältern, mit dem jeweiligen Träger (Fahrzeug bzw. Flugzeug) verbunden. Weist der Träger beim Start der Rakete eine Schräglage auf, so tritt dadurch ein Richtungsfehler der Raketenflugbahn auf. Besonders schwerwiegend wirkt sich die Schräglage dann aus, wenn die Rakete mit nur in einer Richtung wirkenden aerodynamischen Flächen versehen ist, die die Aufgabe haben, die Flugbahn der Rakete in eine bestimmte Richtung zu verändern. Bei Schräglage des Startbehälters würde die Flugrichtung der Rakete verfälscht werden. Daher ist es erforderlich, zum Zeitpunkt des Raketenstarts den Träger in eine horizontale Lage zu bringen. Dies ist bei sich bewegenden Trägern, z.B. Flugzeugen oder Fahrzeugen, nur unvollkommen oder überhaupt nicht möglich.Launch containers for rockets are known which have a guiding device in the form of a plurality of launch tubes, each of which receives a rocket. The guide device is firmly connected to the container housing. The container structure is either movable, for example in the case of rocket launchers mounted on vehicles, or rigidly, for example in the case of launch containers attached to aircraft, connected to the respective carrier (vehicle or aircraft). If the carrier has an inclined position when the rocket is launched, a directional error of the rocket trajectory occurs. The inclined position has a particularly serious effect if the missile is provided with aerodynamic surfaces which act only in one direction and which have the task of converting the missile's trajectory into a specific one Change direction. If the launch container was tilted, the direction of flight of the rocket would be falsified. It is therefore necessary to bring the carrier into a horizontal position at the time of the rocket launch. In the case of moving carriers, for example airplanes or vehicles, this is only incomplete or not possible at all.

Der Erfindung liegt die Aufgabe zugrunde, einen Startbehälter nach dem Oberbegriff des Patentanspruchs 1 so auszubilden, daß er unabhängig von der jeweiligen Lage des Trägers einen Raketenstart in definierter Lage ermöglicht.The invention has for its object to form a launching container according to the preamble of claim 1 so that it enables a rocket launch in a defined position regardless of the respective position of the carrier.

Die Lösung dieser Aufgabe erfolgt erfindungsgemäß mit dem in kennzeichnenden Teil des Patentanspruchs 1 angegebenen Merkmalen.This object is achieved according to the invention with the features specified in the characterizing part of patent claim 1.

Bei dem erfindungsgemäßen Startbehälter ist die Führungsvorrichtung relativ zum Gehäuse drehbar, und eine Stabilisierungsvorrichtung sorgt dafür, daß der Drehwinkel der Führungsvorrichtung in bezug auf das Gehäuse so eingestellt wird, daß etwaige Drehwinkeländerungen des Gehäuses kompensiert werden. Die Führungsvorrichtung nimmt also bezogen auf das Gehäuse einen Drehwinkel ein, der zum jeweiligen Zeitpunkt dem Drehwinkel des Gehäuses relativ zu einem erdgebundenen Referenzsystem entgegengesetzt ist.In the starting container according to the invention, the guide device is rotatable relative to the housing, and a stabilizing device ensures that the angle of rotation of the guide device with respect to the housing is adjusted so that any changes in the angle of rotation of the housing are compensated for. The guide device therefore takes up an angle of rotation with respect to the housing, which at the respective time is opposite to the angle of rotation of the housing relative to an earth-based reference system.

Die Stabilisierungsvorrichtung kann einen Winkeldetektor zur Ermittlung von Drehungen des Gehäuses oder der Führungsvorrichtung in bezug auf das Referenzsystem sowie einen mechanischen Drehantrieb für die Führungsvorrichtung aufweisen. Das Referenzsystem kann bei spielsweise durch einen Kreisel definiert werden, der die Abweichung der tatsächlichen Rollage der Führungseinrichtung vom Soll-Rollwinkel feststellt, wobei der Kreisel entweder im Träger oder im Startbehälter angeordnet sein kann. Als Antriebssystem wird vorzugsweise ein elektromechanisches oder ein elektrohydraulisches System benutzt, jedoch können auch andere Systeme eingesetzt werden, z.B. magnetische, pneumatische oder pyrotechnische Systeme, wobei die benötigte Energie entweder vom Träger geliefert oder im Startbehälter selbst erzeugt wird. Letzteres kann beispielsweise bei Startbehältern an Flugzeugen mittels einer Stauluftturbine und angeschlossenem Stromgenerator bestehen, so daß ein hinsichtlich der Rollstabilisierung völlig autonomer Startbehälter geschaffen werden kann, wenn sich gleichzeitig auch der Winkeldetektor und das die Referenzlage vorgebende System im Startbehälter befinden.The stabilization device can have an angle detector for determining rotations of the housing or the guide device with respect to the reference system, and a mechanical rotary drive for the guide device. The reference system can be used for can be defined, for example, by a gyroscope which determines the deviation of the actual roll position of the guide device from the desired roll angle, the gyroscope being able to be arranged either in the carrier or in the starting container. An electromechanical or an electrohydraulic system is preferably used as the drive system, but other systems can also be used, for example magnetic, pneumatic or pyrotechnic systems, the energy required either being supplied by the carrier or being generated in the starting container itself. The latter can exist, for example, in starter containers on aircraft by means of a ram-air turbine and a connected power generator, so that a starter container that is completely autonomous in terms of roll stabilization can be created if the angle detector and the system specifying the reference position are also located in the starter container.

Im folgenden werden unter Bezugnahme auf die Zeichnungen Ausführungsbeispiele der Erfindung näher erläutert.Exemplary embodiments of the invention are explained in more detail below with reference to the drawings.

Es zeigen:

  • Fig. 1 einen schematischen Längsschnitt durch einen Startbehälter für Raketen,
  • Fig. 2 eine Darstellung des Lageregelsystems für die Führungsvorrichtung,
  • Fig. 3 eine schematische Rückansicht eines Startbehälters, dessen Führungsvorrichtung aerodynamisch stabilisiert wird,
  • Fig. 4 einen schematischen Längsschnitt des Startbehälters nach Fig. 3 und
  • Fig 5 eine ähnliche Darstellung wie Fig. 3 bei Schräglage des Trägers bzw. des Behältergehäuses.
Show it:
  • 1 shows a schematic longitudinal section through a launching container for rockets,
  • 2 shows the position control system for the guide device,
  • 3 shows a schematic rear view of a starting container, the guide device of which is aerodynamically stabilized,
  • Fig. 4 is a schematic longitudinal section of the starting container according to Fig. 3 and
  • Fig. 5 is a view similar to Fig. 3 with the carrier or the container housing in an inclined position.

Der in Fig. 1 dargestellte Startbehälter wird an einem Flugzeug außen angehängt. Er weist ein Gehäuse 1 auf, das mit Aufhängeösen 2 versehen ist und in dem die Führungsvorrichtung 3 angeordnet ist. Das Gehäuse 1 ist an den stirnseitigen Enden offen, und es enthält ringförmige Lager 4, in denen die Führungsvorrichtung 3 um die Längsachse des Gehäuses herum drehbar ist. Die Führungsvorrichtung 3 enthält mehrere Startrohre 5, die sich durch die gesamte Länge des Gehäuses 1 erstrecken und ihren beiden Enden offen sind. Die Startrohre 5 sind mit ihren Achsen auf einem koaxial zur Längsachse des Gehäuses verlaufenden Kreis angeordnet und auf diesem Kreis mit gleichmäßigen Umfangsabständen verteilt.The starting container shown in Fig. 1 is attached to the outside of an aircraft. It has a housing 1 which is provided with suspension eyes 2 and in which the guide device 3 is arranged. The housing 1 is open at the front ends, and it contains annular bearings 4, in which the guide device 3 is rotatable about the longitudinal axis of the housing. The guide device 3 contains several starting tubes 5, which extend through the entire length of the housing 1 and are open at both ends. The starting tubes 5 are arranged with their axes on a circle running coaxially to the longitudinal axis of the housing and distributed on this circle with uniform circumferential distances.

Im Innern des Gehäuses 1 ist ein Servomotor 6 befestigt, dessen Ausgangswelle über ein Zahnrad 7 ein Zahnkranzsegment 8 antreibt, welches an der Führungsvorrichtung 3 koaxial zu dessen Längsachse befestigt ist. Der Servomotor 6 kann somit die in den Lagern 4 gelagerte Führungsvorrichtung 3 um deren Längsachse herum drehen.In the interior of the housing 1, a servo motor 6 is fastened, the output shaft of which drives a sprocket segment 8 via a toothed wheel 7, which is fastened to the guide device 3 coaxially to its longitudinal axis. The servo motor 6 can thus rotate the guide device 3 mounted in the bearings 4 around its longitudinal axis.

In einem an beiden Enden verschlossenen Zentralrohr 9 der Führungsvorrichtung befindet sich das Steuersystem 10,11 zur Rollwinkelstabilisierung. Ein Winkeldetektor 10 gibt an die Steuerelektronik 11 ein Signal, das der Abweichung des Rollwinkels (des Drehwinkels um die Längsachse der Führungsvorrichtung) in bezug auf einen anhand eines erdgebundenen Referenzsystems definierten Soll-Rollwinkel entspricht. Stellt der Winkeldetektor 10 eine Abweichung der Ist-Lage von der Soll-Lage fest, wird von der Steuerelektronik 11 ein entsprechendes Steuerkommando zum Servormotor 6 gesandt, der dann die Führungsvorrichtung 3 um ihre Längsachse dreht, so daß sie unabhängig von der Lage des Gehäuses 1 bzw. des das Gehäuse haltenden Trägers immer den Soll-Winkel einnimmt.The control system 10, 11 for stabilizing the roll angle is located in a central tube 9 of the guide device which is closed at both ends. An angle detector 10 gives the control electronics 11 a signal which corresponds to the deviation of the roll angle (the angle of rotation about the longitudinal axis of the guide device) with respect to a set roll angle defined on the basis of an earth-bound reference system. If the angle detector 10 detects a deviation of the actual position from the target position, the control electronics 11 send a corresponding control command to the servo motor 6, which then rotates the guide device 3 about its longitudinal axis so that it is independent of the position of the housing 1 or the carrier holding the housing always assumes the desired angle.

Fig. 2 zeigt schematisch die Hauptelemente des Startbehälters von Fig. 1 mit den entsprechenden Steuer- bzw. Signalleitungen. Die Führungsvorrichtung 3, die drehbar in dem Gehäuse 1 gelagert ist, enthält das Steuersystem 11,12 mit dem Winkeldetektor 10 und der Auswerteelektronik 11. Der Winkeldetektor 10 ist über Signal- und Energieleitungen 12 mit der Auswerteelektronik 11 verbunden. Von der Auswerteelektronik 11 führt eine Steuerleitung 13 zum Servomotor 6. Die im Flugzeug befindliche Energiequelle 14 ist über Versorgungsleitungen 15,16 mit dem Steuersystem 10 und dem Servomotor 6 verbunden.Fig. 2 shows schematically the main elements of the starting container of Fig. 1 with the corresponding control or signal lines. The guide device 3, which is rotatably mounted in the housing 1, contains the control system 11, 12 with the angle detector 10 and the evaluation electronics 11. The angle detector 10 is connected to the evaluation electronics 11 via signal and power lines 12. A control line 13 leads from the evaluation electronics 11 to the servo motor 6. The energy source 14 located in the aircraft is connected to the control system 10 and the servo motor 6 via supply lines 15, 16.

Fign. 3 bis 5 zeigen eine andere Ausführungsform des Startbehälters, bei der eine aerodynamisch wirkende Stabilisierungsvorrichtung vorgesehen ist. Im Gehäuse 1 mit den Aufhängeösen 2 befindet sich in Drehlagern 4 drehbar gelagert die Führungsvorrichtung 3, die mehrere ringförmig verteilt angeordnete Startrohre 5 enthält. An der Führungsvorrichtung 3 sind zwei V-förmig angeordnete Leitelemente 17 befestigt, die an dem aus dem Gehäuse 1 herausragenden rückwärtigen Ende der Führungsvorrichtung 3 angeordnet sind und seitlich über das Gehäuse 1 hinausragen. Die Leitelemente 17 sind der Außenluftströmung ausgesetzt, die bestrebt ist, die Positionen der Leitelemente 17 beizubehalten und somit Drehungen der Führungsvorrichtung 3 um ihre Längsachse zu verhindern oder auf ein Mindestmaß zu beschränken. Wenn das Flugzeug eine Schräglage einnimmt, der das Gehäuse 1 folgt, so behält die Führungsvorrichtung 3 dennoch ihre Lage im wesentlichen bei, in dem sie sich relativ zu dem Gehäuse 1 in den Lagern 4 dreht. Ein solcher Zustand ist in Fig. 5 dargestellt, wo das Gehäuse 1 eine Schräglage einnimmt, während die Winkellage der Führungsvorrichtung 3 gegenüber Fig. 3 unverändert ist.Fig. 3 to 5 show another embodiment of the starting container, in which an aerodynamically acting stabilizing device is provided. In the housing 1 with the suspension eyes 2, the guide device 3, which contains a plurality of starting tubes 5 arranged in a ring shape, is rotatably mounted in pivot bearings 4. On the guide device 3, two V-shaped guide elements 17 are attached, which on the from Housing 1 protruding rear end of the guide device 3 are arranged and protrude laterally beyond the housing 1. The guide elements 17 are exposed to the outside air flow, which strives to maintain the positions of the guide elements 17 and thus to prevent or minimize rotation of the guide device 3 about its longitudinal axis. When the aircraft is in an inclined position, which is followed by the housing 1, the guiding device 3 nevertheless essentially maintains its position by rotating in the bearings 4 relative to the housing 1. Such a state is shown in FIG. 5, where the housing 1 assumes an inclined position, while the angular position of the guide device 3 is unchanged compared to FIG. 3.

Bei dem Ausführungsbeispiel der Fign. 3 bis 5 ist die Führungsvorrichtung 3 in dem Gehäuse 1 frei drehbar gelagert, ohne daß eine Antriebsvorrichtung vorgesehen wäre. Nimmt das Trägerflugzeug im Flug eine Schräglage ein, so bewirken die auf die Leitelemente 17 einwirkenden aerodynamischen Kräfte ein Moment, das die Füh rungsvorrichtung 3 in der Soll-Lage hält. In the embodiment of FIGS. 3 to 5, the guide device 3 is freely rotatably mounted in the housing 1 without a drive device being provided. If the carrier aircraft takes an inclined position in flight, the aerodynamic forces acting on the guide elements 17 cause a moment that keeps the guide device 3 in the desired position.

Claims (4)

1. Startbehälter für Raketen, mit einem Gehäuse (1), in dem eine Führungsvorrichtung (3) zur Aufnahme mindestens einer Rakete angeordnet ist, dadurch gekennzeichnet, daß die Führungsvorrichtung (3) in dem Gehäuse (1) drehbar ist und daß eine Stabilisierungsvorrichtung (6,7,8,10,11;17) vorgesehen ist, die Drehungen des Gehäuses (1) durch Gegendrehungen der Führungsvorrichtung (3) relativ zu dem Gehäuse ausgleicht.1. launching container for rockets, with a housing (1) in which a guide device (3) for receiving at least one rocket is arranged, characterized in that the guide device (3) in the housing (1) is rotatable and that a stabilizing device ( 6,7,8,10,11; 17) is provided, the rotations of the housing (1) compensated by counter-rotations of the guide device (3) relative to the housing. 2. Startbehälter nach Anspruch 1, dadurch gekennzeichnet, daß die Stabilisierungsvorrichtung (6,7,8,10,11) einen Winkeldetektor (10) zur Ermittlung von Drehungen des Gehäuses (1) oder der Führungsvorrichtung (3) in bezug auf ein erdgebundenes Referenzsystem und einen mechanischen Drehantrieb (6,7,8) für die Führungsvorrichtung (3) aufweist.2. Starting container according to claim 1, characterized in that the stabilizing device (6,7,8,10,11) an angle detector (10) for determining rotations of the housing (1) or the guide device (3) with respect to an earth-bound reference system and has a mechanical rotary drive (6, 7, 8) for the guide device (3). 3. Startbehälter nach Anspruch 1, dadurch gekennzeichnet, daß die Stabilisierungsvorrichtung aus aerodynamisch wirkenden Elementen (17) der Führungsvorrichtung (3) besteht und daß die Führungsvorrichtung (3) frei drehbar in dem Behälter (1) gelagert ist.3. Starting container according to claim 1, characterized in that the stabilizing device consists of aerodynamically acting elements (17) of the guide device (3) and that the guide device (3) is freely rotatable in the container (1). 4. Startbehälter nach einem der Ansprüche 1 bis 3, dadurch gekennzeichnet, daß die Führungsvorrichtung (3) um eine parallel zu der Raketenachse verlaufende Längsachse drehbar ist.4. Starting container according to one of claims 1 to 3, characterized in that the guide device (3) is rotatable about a longitudinal axis running parallel to the rocket axis.
EP87115531A 1986-11-07 1987-10-23 Rocket launch tubes Expired - Lifetime EP0267474B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE19863637986 DE3637986A1 (en) 1986-11-07 1986-11-07 LAUNCHER FOR ROCKETS
DE3637986 1986-11-07

Publications (2)

Publication Number Publication Date
EP0267474A1 true EP0267474A1 (en) 1988-05-18
EP0267474B1 EP0267474B1 (en) 1990-03-14

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EP87115531A Expired - Lifetime EP0267474B1 (en) 1986-11-07 1987-10-23 Rocket launch tubes

Country Status (2)

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EP (1) EP0267474B1 (en)
DE (2) DE3637986A1 (en)

Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2802398A (en) * 1951-01-16 1957-08-13 Lockheed Aircraft Corp Aircraft rocket launcher
US2971731A (en) * 1955-03-10 1961-02-14 Graw Messgerate G M B H Dr Ejection container for radio probes
US4475436A (en) * 1980-04-21 1984-10-09 The Boeing Company Missile launcher

Patent Citations (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2802398A (en) * 1951-01-16 1957-08-13 Lockheed Aircraft Corp Aircraft rocket launcher
US2971731A (en) * 1955-03-10 1961-02-14 Graw Messgerate G M B H Dr Ejection container for radio probes
US4475436A (en) * 1980-04-21 1984-10-09 The Boeing Company Missile launcher

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Publication number Publication date
DE3637986A1 (en) 1988-05-11
EP0267474B1 (en) 1990-03-14
DE3761922D1 (en) 1990-04-19

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